A versatile moon-to-moon transfer design method for applications involving libration point orbits

The objective of the present investigation is to present a framework to produce low-energy trajectories between the vicinities of adjacent moons of a planetary system leveraging libration point orbits in multi-body environments. The current development includes an extension of the Moon-to-Moon Analytical Transfer (MMAT) method previously proposed by the authors, as well as sample applications of transfers between different libration point orbits and planetary systems. The original MMAT technique blends invariant manifold trajectories emanating from libration point orbits in the circular restricted three-body problem to design transfers between distinct moons exploiting some analytical techniques. However, for certain orbital geometries, direct transfers cannot be constructed because the invariant manifolds do not intersect (due to their mutual inclination, distance, and/or orbital phase). To overcome this difficulty, specific strategies are proposed that introduce additional impulsive maneuvers to bridge the gaps between trajectories that connect any two moons. Transfers with one or two intermediate arcs between departure and arrival moons are introduced leveraging a change of plane. When this strategy is still not sufficient to guarantee a transfer, an approach that consists of distant two- and three-burn transfers is introduced. These different strategies are demonstrated through a number of applications of different types in the Jovian, Uranian, Saturnian and Martian systems. Results are also compared with traditional Lambert arcs. The propellant and time-performance for the transfers are illustrated and discussed.